Aeroplane



F. W. BRAUNSCHWEIG.

AEROPLANE.

APPLICATION FILED Aue. n. 1919.

1,379,390. Patented May 24, 1921.

3 SHEETS-SHEET 2 WITNESS: INVENTOR.

@www BY A ATTORNEYS.

UNITED STATES PATENT OFFICE.

FRED W. BRAUNSCHWEIG, OF MILWAUKEE, WISCONSIN.

AEROPLAN E.

To all whom t may concern.'

Be it known that I, FRED WV. BRAUN- SCHWEIG, a citizen of the UnitedStates, and resident of Milwaukee, in the county of M ilwaukee and Stateof Wisconsin, have invented new and useful Improvements in Aeroplanes,of which the following is a description, reference being had to theacconipanying drawings, which are a part of this specification.

The present invention relates to certain new and useful improvements inaeroplanes, and has for one of its objects to provide an aeroplanehaving means for moving its propeller to change its axis of rotationwith respect to the longitudinal axis of the aeroplane whereby to directthe line of flight of the plane.

Another object of the present invention is to provide auniversallypivotally supported passengers seat having means leading therefrom andconnected to the ailerons and elevators whereby the stability of theaeroplane on its lateral longitudinal axis will be maintained as thepassengers seat will at all times seek the center of gravity and in thisway effect the necessary change in the controls to maintain thestability of the-plane. a

Another obj ect of the present invention is to provide means for`collapsibly maintaining the supporting wings in extended position forflight whereby the saine may be readily dropped to lie against the sidesof the nacelle and permit the ready removal of the plane from the fieldto a hangar under its own motive power. Another object of the presentinvention is to provide a transparent portion in the 4g collapsiblewings whereby t e vision of the pilot will not be restricted when thewings are in collapsed position folded against the sides of the nacelle.

Another object of the present invention is to provide a control levercommonly termed joy stick, which is connected with the elevators andrudder and which maynbe connected to means for changing the axis ofrotation of the propeller with respect to the longitudinal axis of theaeroplane whereby the plane will readily respond to manipulation of thecontrols to change the line of flight.

Specicaton of Letters Patent.

Application led August 11, 1919. Serial No.

Patented May 24, 1921.

Another object of the present invention is to provide means for movingthe ground engaging wheels to a position adjacent the sides of thenacelle to thus substantially decrease tlie head resistance of theplane.

Another object of the present invention is to provide means forpivotally supporting the forward ground engaging wheels whereby thedirection of travel of the aeroplane along the ground may be directed atwill.

Another object of the present invention is to provide brake meansconnected with the rear wheels for maintaining the control of the planewhile taxiing.

A further object of the present invention is to provide means secured tothe tip of the propeller for substantially decreasing slippage.

With the above and other objects in view which will appear as thedescription proceeds, my invention resides in the novel construction,combination and arrangement of parts substantially as hereinafterdescribed and more particularly defined 'by the appended claims, itbeing understood that such changes in the precise embodiment of theherein disclosed invention may be made as come within the scope of theclaims.

1n the accompanying drawings I have' illustrated one complete example ofthe physical embodiment of my invention constructed according to thebest mode I have so far devised for the practical application of theprinciples thereof, and in which:

Figure l is a view looking at the front of an aeroplane embodying thevarious features of my invention, the supporting wings being shown indotted lines as folded or collapsed.

Fig. 2 is a side view thereof.

Fig. 3 is a top plan View looking at the interior of the nacelle, partsbeing broken away and in section.

Fig. i is a side view looking at the interior of the nacelle, partsbeing broken away and in section to more clearly illustrate details ofconstruction.

Fig. 5 is a view looking at the rear of the nacelle.

Fig. 6 is a perspective view of the tail surfaces of the plane, and

Fig. 7 is a view of the concave serrated or perforated member formaintaining the lever for changing the axis of rotation of the propellerwith respect to the longitudinal axis of the aeroplane.

Referring now more particularly to the accompanying drawings myaeroplane may be said to consist generally of a nacelle or body 10having a supporting wing surface 11, ground engaging wheels 12, apropelling motor 13, and propeller 14.

The wing surfaces 11 are supported above the nacelle 10 by means ofvertical struts 15, which are connected to the nacelle and to the centersection 16 of the wing surfaces. The center section is also furthersupported or braced by means of a pair of spaced apart struts 17 whichare secured centrally to the nacelle near its forward end and centrallyto the leading edge of the center section. The struts 17 have securedthereto an engine supporting base 18 for universally pivotallyconnecting or securing the engine 13 thereto as will be later described.

As best shown in Figs. 1 and 2, the wing panels 19 have a. pivotalconnection with the center section 16 and are maintained in operativeposition by means of diagonal braces 20 having their outer endspivotally connected to the panels as at 21 medially of their `ends andtheir inner ends pivotally con- 30` nected as at 22 to sliding collarmembers 23 slidably mounted upon the struts 15, the sliding membersbeing connected with means for raising and lowering the same to raiseand lower the wing panels.

The means for raising and lowering the collar members 23 includes ashaft 24 transversely journaled in the nacelle adjacent the foremoststruts 15 and having fixed thereto near each side of the nacelle, asprocket member 25 having a circumferential groove in its periphery, anda plurality of spaced apart recesses. Lach sliding member 23 mountedupon the rear struts 15 has connected thereto, one end of a lifting orraising cable 26 which passes through or is trained about an eyelet orpulley 27 secured to its rear struts 15 and extends forwardly toward theadjacent strut 15 and then through or over the eyelet or pulley 27 andthen down and is secured as at 28 to a hoisting cable 29 which istrained about the adjacent wheel 25 and has one end connected to thebottom of the collar 23 mounted upon the adjacent strut 15 and its otherend passed through or trained about the eyelet or pulley 27 and securedto the top of said collar. The cables 29 have secured thereto aplurality of spaced apart globular enlargements 30 for engagement in therecesses of the wheels 25 so that upon the rotation of shaft 24 thecables 29 will be operated to raise or lower the wing panels as will bereadily apparent. The means for rotating the shaft 24 to raise or lowerthe wing panels comprises a hand wheel 40 mounted thereon adjacent thepilots seat 41 and has its periphery notched or serrated as at 42 forengaging with a pivoted dog or pawl 43 for maintaining the same inadjusted position. The pawl is normally urged to engage the periphery ofthe hand wheel 40 by means of an extensile spring 44, and to permit therelease of the wheel 40 so that the wing panels may be dropped or foldedI provide a release lever 45 connected to the pawl 43 and disposedadjacent the pilots seat as best shown in Figs. 3 and 4.

The rear struts 15 are spaced a slight distance from the rear of thenacelle to form a guideway 30 for the axle 3l of the rear wheels, andthe axle has connected thereto near each rear strut a cable 32 whichpasses over the pulley 33 secured to the adjacent strut and then extendsforwardly along the adjacent side of the nacelle to a pulley 34 and isthen trained about a shaft 35 having its forward end journaled as at 36to the front of the nacelle and its rear end journaled as at 37 to a Tbearing carried by the transverse shaft 24, the shaft being mediallyjournaled or braced as at 38 by a transverse brace member 39 extendingacross the nacelle adjacent the struts 17. W'hen the shaft 35 is rotatedin one direction, the cable 32 will be wound upon the shaft 35 and theaxle 31 raised in the slot 30 to bring the wheels 12 to a position abovethe bottom of the nacelle to reduce head resistance and when the cables32 are being wound upon the shaft 35 a cable 46 which is connected withthe under side of the axle 31 will be unwound, and by this structure itwill be apparent that upon the rotation of the shaft 35 in a reversedirection the axle 31 will be drawn downward to bring the wheels 12 inthe position depicted in the drawings so that the same will be permittedengagement with the ground. The rear wheels 12 have suitable shockabsorbers connected therewith, but as the specific details of the sameconstitute no important part of this invention, the same have not beenshown.

The front wheels 12 are mounted upon spindles 47 pivotally carried bystandards 48 vertically adjustably carried by the forward portion of thenacelle. The standards 48 have inwardly projecting stub shafts 49 whichpass through guide openings in the nacelle and are disposed therein andhave connected therewith suitable shock absorbing springs 50, see Figs.3 and 4.

The standards 48 are adapted to be moved, with the shafts 49 as theirpivots. to a position extending inwardly so that the forward wheels 12will be in a line with the sides of the nacelle when in Hight. The meansfor moving the standards 48 on their pivots include cables 51 having oneend connected with the standards 48 and their other ends wound about theshaft 35. Cables 52 also lead upwardly from the standards 48 and arewound about the shaft 35 in opposite direction from that of the cable 51whereby upon the rotation of the shaft 35 to raise the wheels 12, thestandards 48 will be moved to position the wheels in line with the sidesof the nacelle or vice versa.

The spindles 47 are pivotally connected together by means of atransverse steering rod 53 so that they will work in unison to guide thecourse of the plane along the ground. The spindles 47 are connected to ashaft 54 by means of control or guide cables 55 wound therearound inopposite directions and connected with the arms 47 of the spindles 47.By this structure when the shaft 54 is rotated, the spindles 47 will bemoved on their pivots to guide the wheel and the wheel 56 for rotatingthe shaft 54 is interchangeable with the end of shaft 35 for operatingthe same to position the wheels 12 inside the nacelle. The inner ends ofthe shafts 35 and 54 are squared to receive the wheel 56 and aredisposed juxtaposed the seat 41. The rear wheels have formed thereonsuitable brake drums 57 engaged by brake bands 58 controlled by a lever59 fixed to a shaft 60 adjacent the seat 41 and having leading therefromcontrol `rods or cables 61. By this structure when the lever 59 is drawnrearwardly toward the seat 41, the brakes will be applied so that themomentum of the aeroplane upon the ground may be checked.

The wing panels 19 are equipped with the usual ailerons 62 for directingthe movement of the plane on its longitudinal axis, the ailerons havingupper and lower levers 63 and 64 connected thereto for receiving theends of the usual control wires 65 and 66 respectively. The control wire65 extends across the leading edge of the wing structures and passesthrough or trains about a pulley or eyelet 67 secured to each wing panelnear its leading edge adjacent the levers 63, said wire governing thedrag of the ailerons 62. The control cables 66 are connected withsuitable means for moving the ailerons to maintain the plane at alltimes true on its longitudinal axis. The passengers seat 68 is securedto a cradle 69 which is universally pivotally supported from thetransverse shaft 24 and the transverse brace 70, and as the seat 68 willat all times seek the center of gravity by reason of its universalpivotal suspension the same will move as the plane moves on its lateralor longitudinal axes and the same is connected to the ailerons andelevators so that the same will be operated upon the movement of theseat to maintain the plane at all times stable. The rear member 71 ofthe cradle 69 has leading therefrom two control cables or wires 72 and73 which are connected to lower and upper elevator control levers 74 and75 respectively. By this structure when the seat 68 moves rearwardlywith its cradle 69 by reason of the nose of the aeroplane beingelevated, the control wire 72 will be lengthened and control wire 73shortened to manipulate the elevator 76 to lower the planes nose as willbe readily apparent. A movement of the seat in a forward direction willoperate the rudder in a reverse direction, and the ends of the controlwires 72 and 73 are adjustably connected to the members 71 as at 77, sothat the stabilizing device may be adjusted to agree with the rigging ofthe plane.

Y The aileron control wires 66 are connected to the rear brace member 71of the cradle 69 so that a lateral movement of the cradle 69 due to ashift of the aeroplane on its longitudinal axis will operate theailerons to bring the plane back to a level position. This structureprevents the plane from flying with one wing low and renders the planeinherently stable.

The engine 13 has a substantially universal pivotal connection with itsbase 18 so that the same may be moved in all directions to change theaxis of rotation of the propeller 14 with respect to the longitudinalaxis of the aeroplane and thus assist in directing the line of flightthereof. The movement of the engine 13 with respect to its base isgoverned by means of operating rod 78 which has its lower end pivoted asat 79 to an operating lever 80 universally journaled as at 81 betweenthe struts 17. The movement of the lever 80 in any direction will effecta corresponding movement in the engine 13 and the same is held in anydesired position by means of a pin 82 extending beyond its forward endand engageable with the concave serrated face of a disk member 83. Thecenter of the disk member has an aperture 84 therein so that the centeror true adjustment of the motor 13 with respect to the longitudinal axisof the plane may be readily obtained and a control handle 85 is mountedon the end of the lever 80 adjacent the pilots seat so that the pin 82may be readily held from engagement with the disk 83. The lever 80 maybe moved independently or moved simultaneously with the usual joy stickor control lever 86, and has its end adjacent the pilots seat aperturedto be engaged with the hook or other attaching member 87 formed on theend of the joy stick.

The joy stick inthe present instance 1s universally connected as at 88to a standard 89 disposed in the rear end of the nacelle and in thepresent instance is disposed normally horizontally instead of verticalas in the planes now in use. The joy stick has a pair of laterallyprojecting arms or levers 90 connected therewith from which run thecontrol wires 91 for the rudder 92. The joy stick also has connectedtherewith the control wires 93 connected to the elevators 76independently of the control wires 7 2 and 7 3 connected to thestabilizing seat. As will be readily obvious, the movement up and downor laterally of the joy stick 86 will effect a similar movement in theelevator 7 6 or rudder 92 to direct the line of flight of the plane.

When the joy stick 86 and the lever 80 are coupled together, themovement of the joy stick 86 to turn the rudder to the left to make aleft-hand turn, will also turn the engine 13 on its base to the leftwhereby the torque of the propeller will assist in turning the plane tothe left. In manipulating the elevators to climb or descend, acorresponding movement of the engine on its base will be effected toassist the same. When the joy stick and lever 80 are coupled together acatch or latch 94 will engage, the lever 85 will depress the same towithhold the member 82 from engagement with the disk 83.

As best shown in Figs. 1 and 2, the propeller 14 has formed on its outerends a flange member 14: which projects beyond both the front and rearfaces of the propeller. This structure provides means for reducing to aminimum the slippage of the propeller and thus greatly increases itsefiiciency. In the type of propeller now in common use, a largeproportion of the energy of the propeller is lost due to the slippagethereof and the forming of the flanges 14 serves to reduce this slippageas before stated.

The wing panels 19 are formed on their outer ends with dependingvertical fins 19 which serve to maintain the same on its line of flightwithout side slipping as they offer a resistance to lateral movement aswill be readily apparent. The side fins 19 function much on the order ofthe usual vertical fins employed on a number of modern aeroplanes andlocated at the tail surfaces.

From the foregoing description taken in connection with the accompanyingdrawings, it will be readily apparent that when desired to move theplane from place to place, the wings 19 may be collapsed or folded,seedotted lines, Figs. 1 and 2. In order that the pilot may have anunobstructed view while taxiing along the ground with the wingscollapsed, a suitable transparent portion or window 95 is formed in eachpanel 19 and adjacent the portion thereof juxtaposed the pilots seatwhen folded. This permits the driver to look on. either side or eitherto the front or rear as will be readily apparent.

It will also be apparent that should it be desired to land upon waterthe wheels 12 may be raised, and as the nacelle is water tight, the samemay be used as an ordinary hydroaeroplane.

What I claim as my invention is:

1. An aeroplane including a body, wing panels hingedly connected withsaid body, substantially rigid brace members for maintaining said wingpanels in operative position and having their inner ends connected withthe body and their outer ends connected with the under sides of the wingpanels, said brace members providing means for supporting the wingpanels when the aeroplane is in the air and on the ground, and meansconnected with said brace members for permitting the folding of saidwing panels to a position against the body.

2. An aeroplane including a body, a wing panel hingedly connected withthe body, a brace member having one end pivotally connected with thewing panel outwardly of its hinge connection and its other end slidablyconnected with the body, and means for moving said slidably mounted endof said brace member vertically to fold the wing panel in inoperativeposition and to spread the same in operative position.

3. An aeroplane including a body, a center section supported above thebody, wing panels hingedly connected with said center section, means forfolding said wing panels against the body, and window means in said wingpanels whereby an unobstructed view may be had from the interior of saidbody.

4:. An aeroplane including a body, a center section, supporting strutssupporting said center section above the body, wing panels hingedlyconnected with the center section, diagonal brace members, slidingmembers mounted on said struts, said diagonal brace members having theirinner ends pivoted to said sliding members and their outer endspivotally connected with the wing panels, and means for verticallymoving said sliding members to retain the wing panels in extendedposition when the plane is in Hight and to fold said wing panels againstthe sides of the body when the aeroplane is inoperative.

In testimony whereof, I aiiix my signature FRED W. BRAUNSCHWEIG.

